摘要
近地卫星偏离标称轨道的过程可以表示为该卫星和一个在标称轨迹上运行的"虚"卫星的相对运动,服从Hill方程。在此基础上建立一种在线控制方法,利用模型预测控制(MPC)进行轨道优化和偏差消除,使用多变量优化的控制算法,将控制量的大小与轨道器的轨道偏差联系起来,形成反馈系统,通过给出开环和前馈-反馈闭环两种形式的控制方程,建立基于甚小推力发动机多次点火的轨道控制方法,从而确定控制量将卫星轨道实时保持在偏差管道内。
The process in which the LEO satellite deviates from the nominal orbit can be considered the relative motion between two satellites, i.e. a satellite runs on the actual orbit and a ＂virtual＂ satellite runs on the nominal orbit. It can be described with Hill-equation. An on-line strategy with model predict control （MPC） in state space form was established to optimize the trajectory, and to eliminate the orbit errors. In this strategy, the correct gain with multi-variables which associated maneuver magnitude with the orbit error, written in form of open-loop and close-loop respectively was used to determine the control action series which would constrain the satellite in error box.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2008年第22期6273-6277,共5页
Journal of System Simulation
基金
高等学校博士学科专项科研基金(20060699024)
